View Source SpaceDust.State.KeplerianElements (Space Dust v0.3.0)

Classical Keplerian orbital elements.

Represents an orbit using the six classical orbital elements:

  • Semi-major axis (a): Size of the orbit
  • Eccentricity (e): Shape of the orbit (0 = circular, 0-1 = elliptical)
  • Inclination (i): Tilt relative to the equatorial plane
  • RAAN (Ω): Right Ascension of the Ascending Node
  • Argument of perigee (ω): Orientation of the orbit in its plane
  • True anomaly (ν): Position along the orbit

All angles are in radians. Semi-major axis is in kilometers.

Summary

Types

t()

Functions

angular_momentum(keplerian_elements)

Calculate specific angular momentum magnitude in km^2/s.

apoapsis(keplerian_elements)

Calculate apoapsis radius in kilometers.

from_tensor(tensor, opts \\ [])

Create Keplerian elements from Nx tensor.

mean_motion(elements)

Calculate mean motion in radians per second.

new(semi_major_axis, eccentricity, inclination, raan, arg_perigee, true_anomaly, opts \\ [])

Create new Keplerian elements.

periapsis(keplerian_elements)

Calculate periapsis radius in kilometers.

period(keplerian_elements)

Calculate orbital period in seconds.

specific_energy(keplerian_elements)

Calculate specific orbital energy in km^2/s^2.

to_tensor(keplerian_elements)

Convert Keplerian elements to Nx tensor representation. Returns tensor of shape {6}: [a, e, i, Ω, ω, ν]

true_to_eccentric_anomaly(keplerian_elements)

Convert true anomaly to eccentric anomaly.

true_to_mean_anomaly(elements)

Convert true anomaly to mean anomaly.

Types

t()

@type t() :: %SpaceDust.State.KeplerianElements{
  arg_perigee: float(),
  eccentricity: float(),
  epoch: DateTime.t() | nil,
  inclination: float(),
  mu: float() | nil,
  raan: float(),
  semi_major_axis: float(),
  true_anomaly: float()
}

Functions

angular_momentum(keplerian_elements)

@spec angular_momentum(t()) :: float()

Calculate specific angular momentum magnitude in km^2/s.

apoapsis(keplerian_elements)

@spec apoapsis(t()) :: float()

Calculate apoapsis radius in kilometers.

from_tensor(tensor, opts \\ [])

@spec from_tensor(
  Nx.Tensor.t(),
  keyword()
) :: t()

Create Keplerian elements from Nx tensor.

mean_motion(elements)

@spec mean_motion(t()) :: float()

Calculate mean motion in radians per second.

new(semi_major_axis, eccentricity, inclination, raan, arg_perigee, true_anomaly, opts \\ [])

@spec new(float(), float(), float(), float(), float(), float(), keyword()) :: t()

Create new Keplerian elements.

Parameters

  • semi_major_axis: Semi-major axis in kilometers
  • eccentricity: Orbital eccentricity (0 to < 1 for elliptical)
  • inclination: Inclination in radians
  • raan: Right Ascension of Ascending Node in radians
  • arg_perigee: Argument of perigee in radians
  • true_anomaly: True anomaly in radians
  • opts: Optional parameters
    • :epoch - DateTime for the elements
    • :mu - Gravitational parameter (defaults to Earth)

periapsis(keplerian_elements)

@spec periapsis(t()) :: float()

Calculate periapsis radius in kilometers.

period(keplerian_elements)

@spec period(t()) :: float()

Calculate orbital period in seconds.

specific_energy(keplerian_elements)

@spec specific_energy(t()) :: float()

Calculate specific orbital energy in km^2/s^2.

to_tensor(keplerian_elements)

@spec to_tensor(t()) :: Nx.Tensor.t()

Convert Keplerian elements to Nx tensor representation. Returns tensor of shape {6}: [a, e, i, Ω, ω, ν]

true_to_eccentric_anomaly(keplerian_elements)

@spec true_to_eccentric_anomaly(t()) :: float()

Convert true anomaly to eccentric anomaly.

true_to_mean_anomaly(elements)

@spec true_to_mean_anomaly(t()) :: float()

Convert true anomaly to mean anomaly.